Air-ship.



F. L.- ORR.

AIR SHIP..

APPLIoATIoN FILED sBPT.2a,19os.

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AIR SHIP.

APPLIOATION FILED SEPT,25,1908.

Patented Feb. 9, 1909.

3 SHEETS-SHEET 2.

A TTOHNE YS Patented Feb. 9, 1909.

3 SHEETS-SHEET 3.

.FEMME/5' im? W/TNESSES UNITED sTATEs PATENT oEEicE.

FRANCIS LEONARD ORR, OF OMAHA, NEBRASKA.

' AIR-SHIP.

Specication of Letters Patent.

Patented Fame, 190e.

Application filed Septeinber 25, 1908. Serial No. 454,711.

ject, novel, simple, and improved means whereby to eect buoyancy and propulsion of the vessel. l The invention, in its broad comprehension, comprises an aeroplane, a.basket,car, or

other similar means aiordin'g carrying support, and means consisting of ,al combustion be charged and the; uid

Aso

chamber into whichas, o r other fluid vmay n lcharge be ignited, and the ignited charge liberated through an exhaust o The invention comprehends in details, features of peculiar construction and arrangement enabling the aeronaut to ascend, sail or descend his vessel, and hold it under perfect control.

I would have it understood -that in the practice of my invention, I do not restrict l gitudinally through my invention. Fig. 2 is a transverse section, taken en line 2--2 of Fig. l.` Fi 3-is a similar v1ew,with the aeroplanes own in full lines canted to theA right, and in dotted lines canted to the left. Fig. 4 is an' inverted plan view of the aeroplane, vadjustable fins or wings and the combustion chamber used by me. 5 is a detail sectional view, taken on line 5 -5 of Fig.

4.. Fig. 6 isa similar view, taken on line 6--6 of Fig. 4. Fig-7 isa detail sectional view, taken on line 7--7 of Fig. 1. Fig. 8 is a similar view, .taken on line 8-'8 of Fig. 1, and Fig. 9'is an enlarged'transverse sectional view through the charge conveying pipe used vil-by me, the section being taken through one of the valves on the under side of thev charging pipe.

ening into the air, directly under v the aer'op ane.

l In the practice of my invention I employ edges B curved' downwardly as shown by anaeroplane A, constructed with its side- Figs. Zand 3.

4From the under side of the aeroplaneA, I suspend an elongatedcom'bustion chamber C, the same being attached to the aeroplane by flexible hangers D, shown by Figs. 1

prevent spreading, or enlarging of said eX- 'haust o ening E, I tie its side edges by braces G, the latter being onemember of ghe iiexible hangers D, as clearly shown by 1g. .8. y

0n the under side ofthe aeroplane I arrange va rigid n or rib H, the same being constructed adapted to extend downwardly projecting into t e exhaust port E of the combustion chamber C, as shown byi Figs. 1, 2, 3 and 7 of my drawings.`. The iin I-I maybe secured to the aeroplane by bolts illustrated in Fig. 7, or it`may consist of an integral part of the aeroplane, but obviously I wouldv not restrict myself to any particular means for renderin the n H rigid. The object of the iin H 1s to direct discharge of the ein haust or eX loded ases from one to the other side, .t at is, directing the exitof exploded gases, from one, to the other side of the combustion chamber, according to conditions or comparative angle of the aeroplane and the depending combustion chamber, whereby when the respective positions ofparts are as indicated by Fig. 8, the exhaust gases will be directed to the lowerinost under side oiv theaeroplane, exerting buoyant action effecting to lift said lowermost side of the aeroplane and thereby restore the aeroplane and depending parts to normal or righted positions.

Inside the combustion chamber I arrange an elongated pipe I, andsupport it just below the exhaust lport E, by hangers'd', one thereof being shown by Fig. 8. In the under side of the pipe I, I providea series of openves L, see Figs. 1 and 9. A M indicates asu'pp'ly 'ipe arranged extending from the valve pipe. I toa gas generator, the generator beirg preferably located in a car or cage '0,' pending from .ings K, closed on'the outside, by exible f the combustion chamber C, substantially'as shown by Fig. 1. In this'figure of drawing it will be noticed that a cut-.off valve P 1s provided in the supply pipe M.

In further carrying out my invention, I provide a torch Q, which may consist of any` suitable igniting device, providing continuous blaze adjacent to an opening R, in the combustion chamber, substantially as lshown by Fig. 1. On the under sidel of the aeroplane, I arrange two sets of blades S, having their inner ends hinged to the aeroplane, as indicated by T, adapting themY to be 4folded back adjacent to the combustion chamber C as shown in dotted lines, by Fig. 4. Both sets of the blades S are provi with an operating rod U, ing them to open position, shown by full lines, or to closed folded position indicated by dotted lines. The operating rods U have flexible connection with the blades S, and it is intended that said operating rods U shall be suitably connected with means of any obvious character, located in the -car O, whereby the blades S` may be worked by the aeronaut. as same will be understood. At the rear end of my ship I provide a rudder V of well known cruciform shape, and provide the rud-y der with lateral and vertical adjustment, worked by,an operating rod W made extend ing"y from the rudder into ythe car O,v as shown by Fig. 1, the operating rod W, being supported by any suitable flexible hanger Y The construction of my improved air ship will be understood from the above detail description, but I would have it understood that the detail features maybe changed or modified, without departing from my broadl invention.

. That operation and use of my air shipmay be understood, I will say;- with Athe ship at rest, it becomes necessary supply pipe M.

. Instantl the hot exploded torch Q, and then open the valve I), in the Now 'with the valve l? open as stated, obviously gas will low from the generator N through the pi e M and into the valved pipe I.. Obvious pressureof gas thus supplied will force openl Valves' on the under side of thepipe I permitting the gas to pass into the" combustion.

chamber C. Obviously .the chamberv C will betilled with gas from its wardly, -until the gas reaches the blaze 'of the ignition torch, at which timejthegas charged into the chamber will'be ign upon ignition of the-gas`,1ts1ex plosive orce will close the'flap valves L and thereby, cut of supply of gas throughthe openings K in the pipe I. When a charge o gas in the cham er C has beeny ignited, gas will exhaust or rush out atedl opening E, in the upthrough the elon er Lside of the c by the downwardly curved side edges ded o adapted for work-v I have illustrated no such means,`

to first light the the flapr j top portion down-.`

amberC, and the hot gas- 1 05 ow'out into `the air', directly under4 the aerof -plane with buoyant action on b oth sides of the chamber U adapted to eiect vertical raising of the ship. he liberated hot gas is, in a measure confined under the aeroplane, B on When the exploded gas has about ally passed out 4of the chamber G, a degree of vacuum will be produeedinthe latter, and consequently thereby eiect an in-rush of air, through the opening E, into the chamber (l. Conjointly with lthe above action, the valves L will again be opened by pressure o f gas in the pipes M, I, and therethe aeroplane.

by again ll the chamber C with explosive Y charge, adapted for ignition 1:' the torch Q, as before stated.

From the above statement it will be un derstood that charge after charge of ex' ploded hot gas is fed to the under side of the aeroplane, so long as the valve P, in the pipe M is at open position and by'buoyant action of the hot gas under the aeroplane, the-shipthe air. When the blades will be lifted/into S are adjusted outwardly to inclined position, shown by full lines in Fig. 4, force ofl gas exhausting from the chamber C, to the under side of the aeroplane, will eect pressure against the rear side of the'blades S, thereby operating to force or urge forward movement of the ship. When it is desired to return the air ship to ground, or in sailing movement thereof, the blades S are adjusted to closed position, indicated by dotted lines in Fig. 4, and the valve P closed to cut oi'vlfed of gas to the combustionchamber C. Further description of the rudder or steering means used by me is deemed unnecessary', as the same is of'common knowledge.

Iclaim:A L 1. An' air ship comprising an aeroplane,

a combustion chamber and means adapted to deliver gases from said chamber into the outer air, directly,- under the aeroplane, a

as holder or generatorand means adapted or conveyin gas therefrom, into the comf bustion .cham er, and an igniter whereby to 'ignite gas in the combustion chamber.

2. An air ship comprising an aerop1ane a combustion chamber arranged depending from the aeroplane, the combustion chamber being constructed with an exhaust opening adapted to deliver gasito'the air, directly under the aeroplane, a gas holder. or generator, and means for conveying gas therefrom into the combustionl chamber, and means for igniting gas fed into the combustion chamber.

3. An air yship comprising an aeroplane constructed with downwardly disposed side "edges, a combustion chamber arranged depending from the aeroplane, meansfor exhausting gas" from the combustion chamber into the open air directly under the aero-` plane a gas holder-or generator and means a cut-'ofi valve for conveying gas an igniter, means Afor delivery of ignited gas to the under side of the aeroplane, and blades on the under side of the aeroplane, the blades being provided With means Where- .by tofadjnst them from open to foldedposition, substantially as described.

An air ship comprising an aeroplane, a combustionchamben, arranged depending from the aeroplane, an exhaust port on the upper side of the combustion chamber, a rigid lin on the under side of the aeroplane,

said n being located projecting doWn- Wardly intothe exhaust vport', of the'com-A bustion chamber, a gas holder or generator, an lgnlter, and a Valve controlled passagey Way leading from the generator to said coml bastion chamber.

6. An airship comprising an aeroplane, an explosion chamber, means for holding or generating gas' and delivering the gas into the combustion chamber, means whereby to ignite gas in the combustion chamber, deificesA on the aeroplane located adapted to receive contacting force of the exploded eX` liaust gases and thereby force the air ship forward.

i FRANCIS LEONARD Aonn.

i Witnesses: l

P. C. HERN, PAUL STEIN. 

